Designed by Politechnika Warszawsks, the lightweight open cockpit PW-2D was designed for both factory assembly and as a kit for homebuilding. Of composite construction with fabric covered control surfaces.
Wing span: 11m / 36.1ft
Wing area: 12.7sq.m /136.7sq.ft
Empty Weight: 110kg / 242lb
Payload: 110kg / 242lb
Gross Weight: 220kg / 484lb
Wing Load: 17.32kg/sq.m / 3.55lb/sq.ft
Airfoil: NACA 4415
Aspect ratio: 9.52
MinSink: 1.1 m/s / 3.6 fps / 2.13 kt
L/DMax: 16 69 kph / 37 kt / 43 mph
Seats: 1
The du Temple Monoplane “Canot planeur” of 1874 might have been realized by Félix du Temple de la Croix (1823-1890) from his 1857 patent. The du Temple Monoplane was a steam-powered aircraft made of aluminium, built in Brest, France, by naval officer Félix du Temple.
The aircraft used a very compact, high-speed circulation steam engine for which Félix du Temple applied for a patent on 28 April 1876. The engine used very small pipes packed together to obtain the highest possible contact surface for the smallest possible volume.
When he began with the aid of his brother, M. Louis du Temple, to experiment on a large scale, the inadequacy of all motors then known became apparent. They first tried steam at very high pressures, then a hot-air engine, and finally built and patented, in 1876 a very light steam boiler weighing from 39 to 44 lb. to the horse power, which appears to have been the prototype of some of the light boilers which have since been constructed. It consisted in a series of very thin tubes less than 1/8 in. in internal diameter, through which water circulated very rapidly, and was flashed into steam by the surrounding flame.
This type of boiler, which boils the water instantly, has come to be known as a flash boiler. The engine design was later adopted by the French Navy for the propulsion of the first French torpedo boats.
Variously reported as steam powered or powered by a hot-air engine; fitted with a propeller of 12 blades or 6 blades or even 8 blades; and the undercarriage sometimes claimed as “retracting”.
A flight of the full-scale machine was attempted in 1874 in Brest, where it was launched from a ramp. Several trials were made with the aircraft, and it is generally recognized that it achieved lift-off – described by Dollfus as “short hop or leap” and in Flight International as “staggered briefly into the air” – (from a combination of its own power and running down an inclined ramp), glided for a short time and returned safely to the ground, making it the first successful powered flight in history though not the first self-powered one. Flight was not attained as the machine swiftly hit the ground and rolled over. Reports on who was in the pilot’s seat is given that du Temple at the controls – or, in other reports – a “young sailor” was the pilot.
Félix du Temple had been the first to build a heavier-than-air model (weight 700 g), which flew and landed safely in 1857.
It had a wingspan of 13 m (43 ft) and weighed 80 kg (180 lb) without the pilot.
The Durand biplane features a negative stagger configuration so that it does not produce a full stall, only a very short period of “nibbling” with little loss of altitude. The structure is rated + 3.8 and —1.5 G’s. Roll is produced by a combination of effects when a spoiler is activated, instead of by use of ailerons. According to its designer, a spoiler for roll control actually helps an airplane turn in the direction of the bank, while ailerons do not. The trailing edges of the wings are taken up by full-span flaps. With a standard 150-hp Lycoming, the Durand can carry two people with 128 pounds of baggage at 135 mph over a range of 520 miles. Cockpit controls are basic, with dual sticks in lieu of standard control wheels. The cabin features exceptional visibility by using a forward sliding canopy instead of side doors normally associated with high-wing and biplane cabin aircraft.
Engine 150-hp Lycomlng
HP range: 125-180.
Gross Wt. 1840 lb
Empty Wt. 1210 lb
Fuel capacity 24.5 USG
Wingspan 24 ft 6 in
Length 20 ft 3 in
Top speed 170 mph
Cruise 135 mph
Climb rate 1200 fpm
Ceiling 15,000 ft
Normal range 400 miles
Range with auxiliary tanks 520 mile
Takeoff run 550 ft
Landing roll 450 ft
This was a 2-seat pusher designed and built by Mr. William H. Durand and the aircraft first flew during the Summer of 1948. The all-metal XD-85 was powered by an 85hp Continental C85-12J engine. The aircraft reportedly sustained wing damage in a hangar incident and was not rebuilt. Further development was halted, a fate not uncommon to many other (light) aircraft projects of the immediate post-war years.
This aircraft is a 4 seat aircraft with the prototype (F-PYIT) powered by a Lycoming O320 (160Hp) for the first flight in March 1982. Made available in plans form for home construction and developed from the earlier RD-02 two-seater.
Able to take up to 180hp, the propeller was a variable speed Hoffmann, and autoopilot (badin Crouzet), classified IFR in 1984.
With 23in and 2300rpm it can cruise about 140kt and use 32l per hour (100LL).
Windspan: 8.820m
Length: 6.875m
Wing area: 11.388sq.m
Airfoil: Naca 23019
socket Profil : Naca 23012
Marginal Profil : 6°30′
Dihedral: -3°
Twisted: +3°
Number of seats: 4
Power: 160 HP
Class: Utility
Max speed: 275 km/h
Cruise speed: 253 km/h
Stall speed clean: 105 km/h
Stall speed gear and flaps: 92 km/h
ROC: 5.9 m/s
Max ceiling: 5000 m
Empty weight: 485 kg
Fuel: 108 kg
Passager front weight: 172 kg
Passager rear weight: 154 kg
Luggage: 20 kg
max payload: 443 kg
MAUW: 928 kg
Wing loading: 81.49 kg/sq.m
Power loading: 6.19 kg/hp
Conceived primitively in 1945 of wood, and the construction beginning in 1946, there were disappointments with the Caurite glue. The Office Véritas informed the builders that the plane could not be accepted.
With thoughts of a metallic prototype, the goal was to show that one with 65 cvs. Several years of study and the first drawings done, the framework began at Bessonneau until 1956. The plane was transported at Legrand, where the prototype was finished towards the end of 1961.
The assembly and completion were achieved at the Boos airfield.
July 7, 1962, Edelweiss first flew. Testing by the CNRA was completed June 24. CNRA n° 270952 was delivered August 19, 1963, partner to the file n° 341 of August 23, 1963.
A two-seater, all metal plane, with a Walter-Mikron 4-III motor of 65 hp at 2600 rpm, with retractable tricycle undercarriage.
The Edelweisse was presented to the gathering of the amateur constructors at Rouen-Boos the 16, 17 and 18 August 1963 and made a sensation.
On February 21, 1981, a motor breakdown led Roland Duruble to fit a Revmaster 2100D n°s 2496 of 75 hp, and a twin-bladed metallic constant speed Maloof propeller.
The prop was replaced with a twin-bladed in wood and Revmaster reduced performance to 65 hp at 3200 rpm, although TBO became 1000 hrs instead of 800. Climb rate was noted at + 1,5 m/ses to 11500 ft. The
By October 8, 1984 with 947 hs 25 min TT. the craft wass sold to M. Jacques Plumet. The reported flight time on October 23, 1993 was 1097 hs 39min.
The du Réau Monoplane of 1908 was designed and built using bicycle tubing by du Réau near Angers, France and tested unsuccessfully by Ernest Clairouin.
The basic design of the Cloudcraft Dickson Primary was modified and built by a Mr Dunning, of the Southdown Gliding Club, in 1933-34.
It was first flown from Lancing, UK, on 10 March 1934 only to be written off there on 20 May 1934.
Only one was built and no Certificate of Airworthiness was issued.
Dunne built a monoplane, the D.7, which was displayed at the 1911 Olympia Aero Show in London, and began making de¬liberate attempts to upset the machine’s equilibrium in flight by letting go of the controls during steep, low level turns. Even the most forgiving aircraft will bite when sorely tried, and sure enough Dunne suffered four major crashes for his fool¬hardiness.
Span: 35′
Weight allup: 1400 lb
Speed: 60 mph
A variation of the Baby Ace of the 1930’s, the Dunn D-1 was built in spare time by E.Dunn around 1959. Power is by a Continental A-65 and cruise is 95 mph.
